Summary The pilot and sole occupant of the Bell 206B helicopter (registration C-FGGC, serial number 1080) was departing the Trans North helicopter base on the west bank of the Yukon River at Carmacks, Yukon at about 0700 Pacific daylight time. After lifting off the pad into a low hover facing away from the river, the pilot pedal-turned through 180degrees to the left and departed over the river on an easterly heading. Shortly thereafter, there was a loud impact and splash, and pieces of wreckage drifted down the river. A pilot and two aircraft maintenance engineers, who were preparing a Bell 205 helicopter for flight from an adjacent pad, immediately started the aircraft, tracked the aft fuselage section that was floating down the river, and assisted in its recovery. The submerged forward fuselage section, engine, and transmission were not recovered until located by side-scan sonar on 17 August 2008. The pilot drowned. Ce rapport est galement disponible en franais. Other Factual Information The pilot of C-FGGC was tasked to support the positioning of power poles in the vicinity of Carmacks, Yukon. He was to depart for the job site at around 07001. Another helicopter pilot, flying a Bell205 (registration C-GEAG), was to assist in this operation and was to depart around 0800. Prior to the pilot's arrival at the helipad, a company aircraft maintenance engineer had conducted a routine daily inspection on C-FGGC and fuelled the aircraft with 50United States gallons (USG) of fuel. The pilot arrived and conducted a pre-flight inspection of the aircraft; no defects were reported. He started the aircraft, lifted off, and entered a low hover (about five feet) above the helipad, conducted a 180-degree pedal-turn to the left, and departed to the east, into the sun, directly out over the 800-foot-wide river. The helipad was about six feet above the level of the river; therefore, the initial departure altitude would have been about ten to fifteen feet above the water level. The flight path was directly across the river on a constant descent in a level attitude until the impact with the water surface about 600 feet horizontally from the helipad. Total air time was about 14 seconds. Engine and rotor sounds were normal until impact. The lower fuselage and rear section of the helicopter, containing the floor, rear seats, fuel tank, baggage compartment, and landing gear, remained on the surface of the river and floated downstream until beaching on a sand bar. All other helicopter components were submerged. Eight days later, a boat with a side-scanning sonar found the forward section of the cockpit containing the pilot and the power train in the area of the initial impact with the surface of the river. The pilot was in his seat, secured by his four-point harness, and was wearing a headset but no helmet. The main rotor system had separated from the mast on impact and, although located by the sonar, was not recovered due to operational constraints. Examination of the fracture surfaces on the mast revealed 45 shear lips, indicating overload failure and power being transmitted at impact. The transmission and hydraulic servos remained attached to the deck and were examined to the extent possible. No pre-existing deficiencies were found. The tail boom and tail rotor assembly were not located. The airspeed indicator was indicating about 40 knots, the torque gauge was indicating 100per cent, and the altimeter was indicating about 5250feet above sea level (asl). All other instruments had reverted to zero or were impact-damaged. The engine had sustained a main rotor blade strike on top of the combustion chamber, separating the gas generator section from the gearbox. The fuel cell was intact and about 50USG of fuel were recovered. Residual fuel on board prior to fuelling was not determined. The pilot was certified and qualified for the flight in accordance with existing regulations. He had approximately 23000hours of total flying time. The pilot had not flown in the preceding 24hours, but had accumulated a total of 116.6hours in the preceding 30days and 285.0 ours in the 90days before the occurrence. These hours are within the regulatory limits. The pilot's licence was validated with a Category 1 medical certificate issued on 07May 2008 and valid to 01November 2008, with the condition that glasses must be available. The pilot would normally be wearing his glasses during the start up and departure phases of flight. He was not wearing sunglasses. Autopsy results revealed non-life-threatening fractures and injuries to ribs, pelvis, and right leg, and no significant head injuries. The cause of death was by drowning. Also found was severe, multifocal coronary artery atherosclerosis with no obvious sign of acute infarction. Based on medical opinion, pilot incapacitation does not appear to have been a factor in this occurrence. Weather conditions at Carmacks as observed by an automated weather observation system (AWOS) at the time of the occurrence were as follows: winds 350 true (T) at 2knots, temperature 3C. Most of the flight and the impact were recorded with a low-resolution video camera taken from the river bank about one-half mile upstream from the occurrence site. The section of river, from the helicopter pad to the campground where the video was taken, is straight and oriented due north and south (about 350-degrees T). Water current speed was about 11knots, with no wave action. While clear sky conditions were present, there was a trace of light mist over the river. The sun was just above the ridge and trees, directly to the east across the river, and was reflecting brightly off the surface of the river. The helicopter's intended flight path would have been directly into the sun. The sun's angle was calculated to be about 15degrees above the pilot's horizontal reference, and the reflection of the sun in the water to be about 15degrees below the pilot's horizontal reference. The US Department of Transportation Federal Aviation Administration (FAA) report number DOT/FAA/AM-03/6 defines glare as a temporary visual sensation produced by luminance (brightness) within the visual field that is significantly greater than that to which the eyes are adapted. The report queried the US National Transportation Safety Board Aviation Accident/Incident Database from 01/01/1988 to 12/31/1998 for terms related to glare including sun, glare, vision, blinded, and reflections. For the study period, there were 130accidents in which glare from natural sunlight was found to be a contributing factor, with 55per cent associated with the takeoff/departure and approach/landing phases of flight. Somatogravic illusion is an erroneous sensation of pitch (rotation in the vertical plane) caused by linear acceleration or deceleration. It is a common phenomenon during rapid acceleration or deceleration as would be experienced during an aircraft's takeoff, initial climb, or descent. Analysis of the video revealed that the helicopter had accelerated from zero to 40mph in less than 14seconds, which is sufficient to produce the sensation of about 8.5degrees of pitch-up in the absence of visual clues as to actual attitude if linear acceleration is assumed.